Complex Thermal Analysis of Solid Rocket Propellants

摘要

The paper presents results of experimental research of selected solid rocket propellants with the use of modern thermal analysis techniques. Differential Scanning Calorimetry (DSC) was used to determine specific heat values in the temperature range from -100 °C to 100 °C with the heating rate of 10 K/min. Simultaneous thermal analysis (STA) involving differential thermal analysis and thermogravimetry allowed the detailed analysis of the thermal decomposition process of solid rocket propellants. Dilatometry (DIL) experiments were used to study the thermal expansion of the propellants and to determine the coefficients of linear thermal expansion. Dynamic mechanical analysis (DMA) enabled to study the changes in the mechanical properties in the temperature range from -120 °C to 110 °C as well as to determine the glass transition and softening temperatures of the propellants. The values of these temperatures set the limit of safe operation of solid rocket propellants. In all cases the main goal of the conducted experiments was to present key testing parameters of each thermal analysis method required to obtain reliable results. DSC, STA, DIL and DMA techniques form a complex thermal analysis allowing detailed characterization of solid rocket propellant properties.